Facilitating learning adaptive V-tail of a supersonic missile for radar cross-section reduction during interval flight

Zhou, Zeyang; Huang, Jun

doi:10.1016/j.heliyon.2023.e20984

Heliyon

2023

DOI: 10.1016/j.heliyon.2023.e20984

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Facilitating learning adaptive V-tail of a supersonic missile for radar cross-section reduction during interval flight

Zeyang Zhou,

Jun Huang

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2024

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Cited by 2 publications

References 31 publications

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Unsteady aerodynamic characteristics of a morphing tail configuration

Jiang,

Chen,

Yang

et al. 2024

Physics of Fluids

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Morphing aircraft is an important trend in the future development of next-generation aircraft. This paper focuses on aircraft with a small aspect ratio flying wing configuration that includes morphing tails. The unsteady aerodynamic characteristics of the morphing tail configuration are numerically simulated using the unstructured overset grid technique and the dual-time method, focusing on the effects of the tail deflection angle over time, Mach number, and side slip angle on the unsteady aerodynamic characteristics of the entire aircraft and tails. The second derivative of the tail deflection angle with time should be continuous, and the maximum angular velocity and maximum angular acceleration should be minimized. The hysteresis loop area is closely related to the Mach number. The sideslip angle aggravates the nonlinearity of the unsteady aerodynamic characteristics of the entire aircraft. The unsteady aerodynamic characteristics during tail morphing are affected by static (wing downwash effect and projected area effect) and dynamic (flow field hysteresis effect, additional motion effect, and wall implication effect) characteristics. The enclosed research provides a reference for the aerodynamic and control system designs of morphing tail configurations.

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Unsteady aerodynamic characteristics of a morphing tail configuration

Jiang,

Chen,

Yang

et al. 2024

Physics of Fluids

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Aerodynamic Optimization and Characterization of a Ducted Tail for a Box-Launched Aircraft

Jia,

Zheng,

Zhou

et al. 2024

Applied Sciences

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The tail wing of box-launched aircraft needs to be folded in the launch box, which can easily cause malfunctions during flight deployment. This article presents a ducted tail wing aircraft that does not require folding of the tail wing. To address the nonlinear problem of lift coefficient in the ducted tail, an aerodynamic optimization method for ducted tails based on the sparrow search algorithm with back-propagation (SSA-BP) neural network approximate model and multi-objective genetic algorithm fusion is proposed, with the goal of improving the lift-to-drag ratio and linearization degree of the lift curve. The linearization degree of the optimized tail lift coefficient curve is significantly improved, and the lift-to-drag ratio is significantly improved under cruising conditions. Based on this optimization result, the shape of the tail wing and fuselage combination was optimized, and the optimal configuration of the ducted tail wing aircraft was selected, providing a reference for the design of ducted tail wing aircraft.

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Facilitating learning adaptive V-tail of a supersonic missile for radar cross-section reduction during interval flight

Cited by 2 publications

References 31 publications

Unsteady aerodynamic characteristics of a morphing tail configuration

Unsteady aerodynamic characteristics of a morphing tail configuration

Aerodynamic Optimization and Characterization of a Ducted Tail for a Box-Launched Aircraft

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